Guillotine separation joint



y 1964 J. N. STEINMETZ, JR., ETAL 3,131,635

GUILLOTINE SEPARATION JOINT Filed Oct. 15, 1961 2 Sheets-Sheet 1 I6 FIG. 3

INVENTORS JOSEPH N. STEl/VMETZJR. LEO V. G'ILADETT ATTORNEYS May 5, 1964 J. N. STEINMETZ, JR., ETAL 3,131,635 cumo'rms SEPARATION JOINT 2 Sheets-Sheet 2 Filed Oct. 13, 1961 INVENTORS JOSEPH N. STE/NMETLJR LEO Pl GILADETT -O n/ m A ATTORNEYS United States Patent 3,131,635 GUILLOTINE SEPARATION JOINT Joseph N. Steinmetz, In, Santa Clara, and Leo V. Giladett,

Santa Cruz, Caiiti, assignors, by mesne assignments, to

the United States of America as represented by the Secretary of the Navy Filed Oct. 13, 1961, Ser. No. 145,008 11 Claims. (Cl. 102-49) The present invention relates to an apparatus for produc ng shear failure in metallic components, and more particularly, to an apparatus for producing shear failure in the metal skin of a missile for effecting the separation of component parts of the missile.

In the past separation has been accomplished by the employment of an externally disposed segmental ring of channel cross section provided with confronting inner surfaces which are adapted to engage sloping surfaces formed on outwardly extended flanges on a rocket motor and a forwardly attached component, respectively, for holding the motor and component together. The segments of the ring are interconnected by explosive bolts which are adapted to be detonated when the release of the segmental ring and separation of the component from the motor is desired. Such separation apparatus has projecting parts which do not make for a smooth outer skin of the motor and its component thereby adding to the drag of the missile in flight.

Separation has also been accomplished by the use of a releasable locking means for detachably securing together a booster rocket motor and a forwardly attached component, utilizing explosively actuated means for releasing the locking means. The locking means is disposed inwardly of the outer skin of the motor-component system and is adapted to unlock upon the release thereof, thereby to effect positive and smooth separation of the component from the motor. The separation apparatus makes use of a plurality of such explosively actuated means thereby complicating an already complicated system.

The instant invention provides for separation between a booster rocket motor and a forwardly attached component by the use of an annulus of a mild detonating fuze such as Primacord placed in juxtaposition with one surface of an interconnection between the rocket components. A sharp element is placed against the opposite surface of the innor connection so that detonation of the explosive severs the interconnection circumferentially by a guillotine action thereby effecting separation of the missile component. Such separation accomplishes a clean shear failure without the use of any moving parts, eliminates fragments and provides for better sock isolation. The use of a stationary cutting edge together with the explosive force of a mild detonating fuze for producing a clean failure offers simplicity in that there is only one active element, the mild detonating fuze, for effecting the entire guillotine action.

Therefore, an object of the present invention is the provision of a mild detonating force for shearing an element by providing shock pressure energy against such an element which is placed against a cutting edge.

Another object is to provide by shock pressure energy a clean shear failure without the use of any moving parts.

A further object of the invention is the provision of shock pressure energy to provide a clean shear failure while avoiding the production of fragments.

Still another object is to provide an improved and reliable connection between a booster motor and another missile component.

Yet another object of the present invention is the provision of an improved separation joint between missile components which permits separation of one missile component from the other without applying to the component,

3,131,635 Patented May 5, 1964 ice during separation, deflecting forces which would cause departure from the desired ballistic projectory intended.

A still further object is to cleanly shear the interconnection of missile components by a mild detonating fuze producing shock pressure energy against such an interconnection which is maintained against the cutting edge without the production of fragments and providing shock isolation.

Other objects and many of the attendant advantages of this invention will be readily appreciated as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein:

FIG. 1 is an exploded perspective view of a ballistic missile system with which the separation means of the present invention is associated;

FIG. 2 is a diagrammatic view illustrating the function of the separation means of this invention during the flight of the missile system;

FIG. 3 is a fragmentary side view of the missile system showing the joint between the missile component and the booster motor;

FIG. 4 is the cross section of the annular separation joint;

FIG. 5 is, in perspective, a modification of the present invention for shearing sheet metal.

Referring now to the drawings wherein like referenced characters designate like or corresponding parts throughout the several views, there is shown in FIG. 1 a ballistic missile system with which the separation means of the instant invention may be associated.

The components of the missile system are shown separated for a better understanding thereof. The missile system comprises a first stage solid propellant rocket booster motor 11 having propulsion control means 12, a second stage solid propellant rocket booster motor 13 with its propulsion control means 14, and an interconnecting skirt section 15 which joins the rocket motors 11 and 13 and is adapted to contain means 21 for separating the first stage motor 11 and skirt section 15 from the remainder of the missile system. Forward of the second stage motor 13 is an equipment section 16 to which a ballistic missile or re-entry body 17 is detachably connected by the instant invention. The nose of the re-entry body is provided with a nose fairing 18. It will be understood, of course, that the several components of the missile system are adapted to be connected together and that the equipment section 16 houses suitable guidance and control mechanisms operatively connected to the propulsion controls and separation means for guiding the system along the proper booster trajectory or flight path and for separating the positions of the systems as is necessary for delivering of the missile component or re-entry body 17 to the intended target.

Turning now to FIG. 2 for a better understanding of the flight of the missile system and the function of the separation means of the instant invention in such flight, the missile system is shown as being ejected from a submerged submarine 19. Alternatively, however, it could be launched from a surfaced submarine, surface missile or fiom dry land if desired. Timed with the launching of the missile system is the ignition of the first stage motor 11 as best seen in FIG. 2.

Upon burn out of the first stage motor 11, first separation is effected as best seen at B of FIG. 2. Such separation can be effected by a loop or Primacord 21 juxtaposed to the internal surface of the shirt section 15 with the P-rimacord being detonated at the proper time by control mechanisms in the equipment section 16 which are responsive to the burning out or tail-off of the motor 11. Alternatively, a separation joint equivalent to the separa- .3 tion joint 22 of the instant invention could be employed rather than merely employing the loop or Primacord 21 to separate skirt from motor 13.

After the first separation, the first stage motor 111 falls off and the second stage motor 13 continues on its guided trajectory toa point where the velocity and the direction of the re-entry body are such that, if free from the second stage motor, the ballistic missile or re-entry body 17 would follow a ballistic trajectory intersecting the target T. At this point as best seen at C of FIG. 2 the second separation and thrust combination occur in response to appropriate signals from the control mechanism in the equipment 16. The second separation is accomplished by the instant invention at the separation joint 22 of FIG. 3. After the second separation the second stage motor 13 :and attached equipment section 16 fall away from the re-entry body 17 which continues on its unguided or ballistic trajectory to target T.

The upward flight of the ballistic missile or re-entry body 17 carries it through the outer reaches of the earths atmosphere and beyond the mesosphere. The nose fairing 18 is provided to protect the nose of the re-entry body 17 during passage through the lower, thicker regions of the earths atmosphere. Prior to the re-entry of the ballistic missile 17, nose fairing 1 8 is forestalled or jettisoned in response to ambient conditions in the upper rarefied atmosphere, as best seen at D in FIG. 2. The nose fairing is needed only for the upward flight and thus unnecessary during re-entry because of the design of the reentry body.

It will be appreciated that after the second separation the ballistic missile 17 is no longer powered or guided and so if deflecting forces are exerted upon the re-entry body it could cause departure from the intended ballistic trajectory. It is, therefore, important that deflecting forces be absent or at least minimized at the second separation so that the ballistic missile will proceed to the target. Thus, the second separation must be as smooth as possible. The separation means of the present invention is designed to effect smooth separation of the ballistic missile from its propulsion means.

For a detailed description of the separation means of the present invention reference is made to FIG. 4 showing a cross-sectional view of the separation joint between the equipment section 16 and the re-entry body 17. The separation joint '22 comprises an element connected to the re-entry body 17 by means of a countersunk bolt 31 and nut 32. Portion 30 of separation joint 22 has a rearwardly annular flange 33. A second component 34 of the separation joint 22 is connected to annular flange 33 by a bolt .35 and nut 36. The annular portion 34 is adapted by an opening 37 to be bolted to the equipment section 16. Portion 30 of the separation joint 22 has a radial projection 50 which projects into abutting juxtaposition with the end of re-entry body 17 and an end of the component 34. Between the nut 36 and the annular flange 33 is maintained a firing block 40 having a groove 41 therein along the surface contacting the annular flange 33 so that a mild detonating fuze such as Primacord 42 may be inserted therein. On the opposite side of the annular flange 33 from the cavity 41 is a second cavity 44 in the component 34. The forward wall of the cavity 44 terminates in a sharp cutting edge 43 fixedly positioned against the root of flange 33 at its outer diameter by bolt 35 and nut 36. Element 34 has a second cavity 45 along its surface abutting the projection of element 30 for placement therein of an 'O-ring 46 or other suitable airtight element.

It should be understood that re-entry body 17, element 30, element 34, firing block 46, and the flange 3 3 as well as the cavities 41, 43, and 44 are all annular and conform to the annular characteristics of the missile. Thus, a plurality of bolts 31, 35 and openings 37 are also required about the circumference of these elements in order to adequately fasten the missile components into a unitary construction. It should also be understood that the bolt 35 could be countersunk as is bolt 31 so as to provide a more perfect aero-dynamic surface.

A second modification of the invention as best seen in FIG. 5 sets forth the shearing of a sheet '52. While the device in FIG. 5 is employed to shear a flat sheet 52, it may be designed to conform to various configurations so as to shear variations of metallic elements. The shearing device as set forth in FIG. 5 operates on exactly the same basis as the separation joint set forth in FIG. 4. A plurality of bolts 56 and nuts 57 are employed in a plurality of apertures in the firing block 53, the metallic sheet 52 and the guillotine chamber 50 so as to clamp the various elements together in the same manner as bolt 35 and nut 36 clamp elements 30, 34 and 4t) together in FIG. 4. The guillotine chamber 50 has a groove therein along the surface which contacts the metallic sheet 52 and also has the sharp edge along a wall of the cavity 51. The firing block 53 at groove 54 for the insertion of a mild detonating fuze or Primacord along the surface of sheet 52 opposite the cavity 51 in the guillotine chamber 50 so that detonation of the detonating fuze will cause shearing of the metallic sheet along a line described by the sharp edge of the groove 51. While FIG. 5 illustrates the clamping of the guillotine chamber 50 to the sheet 52 and the firing block 53 by plurality of bolts along the length of the elements of the shearing device, it should be understood that any of the common and well known clamping methods could be employed to satisfactorily hold the elements in their operative positions.

Summarizing briefly, the instant invention provides a novel device for shearing a metallic sheet or annular member in such a manner as to provide a clean shear failure without the use of any moving parts while eliminating fragments and providing satisfactory shock isolation. In the separation of missile components the shearing is accomplished in such a smooth manner as to permit the re-entry body to separate from the equipment section 16 smoothly and with very little or no vibration.

This smooth separation of isolated shock vibration enables the ballistic missile to maintain its predetermined trajectory to its ultimate target.

Obviously, many modifications and variations of the present invention are possible in light of the above teachings. It is, therefore, to be understood that within the scope of the appended claims the invention may be practiced otherwise than as specifically described.

What is claimed and desired to be secured by Letters Patent of the United States is:

1. A shearing device comprising a first member having a first groove and a cutting edge formed from a Wall of said first groove; a second member having a second groove; means for fixedly positioning said first and second members so that said first and second grooves are held in alignment on opposite surfaces of a member to be sheared; and means disposed in said second groove for producing shock pressure whereby said member to be sheared fails cleanly along said cutting edge.

2. A shearing device comprising a guillotine chamber having a first groove and a guillotine edge formed by a wall of said first groove, a firing block having a second groove, clamping means for clamping said guillotine block and said firing block to a member-to be sheared so that said first and second grooves are aligned and face onto opposite surfaces of said member to be sheared, and a detonating fuze disposed in said second groove to provide shock pressure upon detonation suflicient to cause shearing along said guillotine edge.

3. A shearing device as claimed in claim 2 wherein said detonating fuze comprises a mild explosive.

4. A separation joint for causing separation of two interconnected elements comprising a first member connected to one of said interconnected elements and having a body portion and a flange portion; a second member connected to the other of said interconnected elements and having a first groove abutting a first surface of said flange, a cutting edge formed from a wall of said first groove, 21 second groove abutting said body portion of said first member; means disposed in said second groove for causing the abutment of said first and second members to be airtight; a third member having a third groove abutting a second surface of said flange at a point opposite said first groove; means for fixedly maintaining said second member, said flange, and said third member in juxtaposed relationship; and means disposed in said third groove for producing shock pressure on said flange whereby said flange is sheared along said cutting edge thereby causing separation of said first and econd interconnected elements.

5. A separation joint as claimed in claim 4 wherein said means disclosed in said third groove comprises a mild detonating fuze.

6. A separation joint as claimed in claim 5 wherein the means disposed in said second groove for causing an airtight abuttment is an O-ring.

7. A separation joint as claimed in claim 6 wherein said first, second, and third members, said flange, said first, second and third grooves, said mild detonating fuze, and said O-ring are annular.

8. A separation joint as claimed in claim 7 wherein said means for fixedly maintaining said second member, said flange, and said third member in juxtaposed relationship comprises a plurality of bolts spaced radially through the circumference of said fixedly maintained elements.

9. In a missile of the type having separable components, separation means connecting a pair of said components together, said separation means comprising a first part connected to a first of said components and having a body portion and a flange portion, a second part connected to a second of said components and having a first groove abutting a first surface of said flange portion, a guillotine edge formed from a wall of said first groove, a second groove abutting said body portion of said first part, means to maintain the abuttment of said body portion and said second part in airtight condition, a third part having a third groove in contact with said flange and aligned with said first groove, means for clamping said second part, said flange member, and said third part together and mild detonation means disposed in said third groove for providing shock pressure whereby said flange is sheared along the guillotine edge of said first groove.

10. In a missile as set forth in claim 9 wherein said first part, second part, and third part, said flange portion, said first, second, and third grooves, said mild detonating means, and said means to maintain the abutment of said body portion and said second part in airtight condition are annular.

11. A missile as set forth in claim 10 wherein said means for clamping comprises a plurality of bolts extending radially through the circumference of said second part, said flange member, and said third part.

Toelke Dec. 16, 1952 Kratzer Aug. 22, 1961 

1. A SHEARING DEVICE COMPRISING A FIRST MEMBER HAVING A FIRST GROOVE AND A CUTTING EDGE FORMED FROM A WALL OF SAID FIRST GROOVE; A SECOND MEMBER HAVING A SECOND GROOVE; MEANS FOR FIXEDLY POSITIONING SAID FIRST AND SECOND MEMBERS SO THAT SAID FIRST AND SECOND GROOVES 